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采用大涡模拟技术,针对某分段式固体火箭发动机开展了发动机燃面退移0mm,160mm和280mm三个时刻下发动机燃烧室内部流动不稳定现象的数值分析,获得了三个典型时刻燃烧室内压强可能的振荡特性。计算结果表明,在发动机点火初期燃烧室内流动不稳定性主要由表面涡脱落导致;随着燃面的退移,端面限燃层暴露在燃气中,由于端面包覆结构残余的影响,燃烧室内流动不稳定性主要由障碍涡脱落决定,且与点火初期相比,压强振荡的频率逐步减小。
The large-eddy simulation technique was used to analyze the instability of the internal combustion engine chamber at 0, 160 and 280 mm for the stationary solid rocket engine. Three typical moments of combustion chamber Possible oscillation characteristics of pressure. The calculation results show that the instability of the flow in the combustion chamber is mainly caused by the surface vortex shedding during the initial ignition of the engine. As the combustion surface is retreated, the end-limited combustion layer is exposed to the gas. Due to the residual influence of the cladding structure, the flow in the combustion chamber The instability is mainly determined by the failure of the vortex shedding, and the frequency of the pressure oscillation is gradually reduced compared with the initial ignition.